摘要
采用基于雷诺平均的二维N-S方程和RNGk-ε湍流模型对二元喷管喉道气动偏转矢量控制时的流场进行了数值模拟,计算结果表明在小扩张比、短扩散段喷管上,在喉道气动偏转矢量控制方案下主流可以实现亚声速偏转。在此基础上数值分析了喉部和扩散段射流流量的分配对喷管流场的影响,研究表明要获得更大的推力矢量角,应该将更多的流量分配在扩散段射流缝处,经过计算得到较佳的扩散段射流流量和喉部射流流量分配比例大约为3∶1。
Different convergent-divergent nozzle flow fields were calculated with 2D Reynolds average N-S equation by the finite volume method and RNG κ-ε turbulence model. The results show that the subsonic turning is achieved on the small nozzle expansion area ratios and short nozzle flap lengths. Based on these results, the effect of jet flow distribution on the throat and flap length were further analyzed. To get more thrust vector angle, more jet flow should be distributed to the slot on the flap length, and better jet flow distribution ration on the flap length and throat is 3：1.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2008年第1期58-61,共4页
Journal of Propulsion Technology
关键词
喉道气动偏转
射流分配
推力矢量
喷管流场
Fluidic throat skewing
Jet flow distribution
Thrust vectoring
Nozzle flow field
